2016-02-04: Turbine rear frames (TRFs)

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for parthttp//www.continentalsanantonio.com 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2016-02-04 CFM International S.A.: Amendment 39-18383; Docket No. FAA-2015-2893; Directorate Identifier 2015-NE-20-AD. (a) Effective Date This AD is effective March 1, 2016. (b) Affected ADs None. (c) Applicability This AD applies to CFM International S.A. (CFM) CFM56-5B engines with turbine rear frame (TRF), part number (P/N) 338-102-907-0 or P/ N 338-102-908-0, installed. (d) Unsafe Condition This AD was prompted by a corrected lifing analysis by the engine manufacturer that shows the need for an initial and repetitive inspection of certain P/N TRFs on the low-pressure turbine (LPT) frame assembly. We are issuing this AD to prevent failure of the TRF on the LPT frame assembly, which could lead to engine separation, damage to the engine, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) For Engines that have Applied CFM Service Bulletin (SB) No. CFM56-5B S/B 72-0308: (i) Prior to accumulating 25,000 cycles since new (CSN) on the TRF of the LPT frame assembly or within 150 cycles after the effective date of this AD, whichever occurs later, perform an initial eddy current inspection (ECI) or a fluorescent penetrant inspection (FPI) of the TRF mount struts on the LPT assembly. (ii) For engines with unknown CSN on the TRF of the LPT frame assembly, perform the initial inspection required by this AD within 150 cycles-in-service (CIS) after the effective date of this AD. (iii) Use paragraph 3.B. in the Accomplishment Instructions of CFM SB No. CFM56-5B S/B 72-0850, dated December 19, 2012, to do the ECI and paragraph 3.C. in the Accomplishment Instructions of CFM SB No. CFM56-5B S/B 72-0850, to do the FPI. Do not include TRF mount strut crack lengths towards the cumulative crack length after the cracks are repaired. (iv) If no cracks are found on any of the three TRF mount struts, repeat the inspection within 1,670 cycles since last inspection (CSLI) or prior to accumulating 25,000 CSN on the TRF of the LPT assembly, whichever occurs later. (v) If the cumulative length of all cracks found at any TRF mount strut location is less than 0.20 inches, repeat the inspection within 1,670 cycles CSLI. (vi) If the cumulative length of cracks found at any TRF mount strut location is greater than or equal to 0.20 inches, but less than 0.25 inches, repeat the inspection within 280 CSLI. (vii) If the cumulative length of cracks found at any TRFmount strut location is 0.25 inches or greater, replace the TRF with a part eligible for installation before further flight. (2) For Engines that have Not Applied CFM SB No. CFM56-5B S/B 72-0308: (i) Prior to accumulating 32,000 CSN on the TRF of the LPT frame assembly or within 150 cycles after the effective date of this AD, whichever occurs later, perform an initial ECI or FPI of the TRF mount struts on the LPT frame assembly. (ii) For engines with unknown CSN on the TRF of the LPT frame assembly, perform the initial inspection required by this AD within 150 CIS after the effective date of this AD. (iii) Use paragraph 3.B. in the Accomplishment Instructions of CFM SB No. CFM56-5B S/B 72-0850, dated December 19, 2012, to do the ECI and paragraph 3.C. in the Accomplishment Instructions of CFM SB No. CFM56-5B S/B 72-0850, to do the FPI. Do not include TRF mount strut crack lengths towards the cumulative crack length after the cracks are repaired. (iv) If no cracks are found on any of the three TRF mount struts, repeat the inspection within 2,500 CSLI or prior to accumulating 32,000 CSN on the TRF of the LPT assembly, whichever occurs later. (v) If the cumulative length of cracks found at any TRF mount strut location is less than 0.20 inches, repeat the inspection within 2,500 CSLI. (vi) If the cumulative length of cracks found at any TRF mount strut location is greater than or equal to 0.20 inches and less than 0.25 inches, repeat the inspection within 370 CSLI. (vii) If the cumulative length of cracks found at any TRF mount strut location is 0.25 inches or greater, replace the TRF with a part eligible for installation before further flight. (f) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: ANE-AD-AMOC@faa.gov. (g) Related Information (1) For more information about this AD, contact Kyle Gustafson, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7183; fax: 781-238-7199; email: kyle.gustafson@faa.gov. (2) CFM SB No. CFM56-5B S/B 72-0308, which is not incorporated by reference in this AD, can be obtained from CFM, using the contact information in paragraph (h)(4) of this AD. (h) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on March 1, 2016. (i) CFM International S. A. (CFM) Service Bulletin No. CFM56-5B S/B 72-0850, dated December 19, 2012. (ii) Reserved. (4) For CFM service information identified in this AD, contact CFM International Inc., Aviation Operations Center, 1 Neumann Way, M/D Room 285, Cincinnati, OH 45125; phone: 877-432-3272; fax: 877- 432-3329; email: aviation.fleetsupport@ge.com. (5) You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. (6) You may view this service information at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call [[Page 4174]] 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.